中国空间科学技术

中国空间科学技术 ›› 2021, Vol. 41 ›› Issue (2): 55-62.doi: 10.16708/j.cnki.1000-758X.2021.0022

• 研究探讨 • 上一篇    下一篇

火星表面热环境对航天器热控影响分析

张冰强，向艳超，薛淑艳，郑凯，钟奇，张有为   

  1. 1 北京空间飞行器总体设计部，北京100094
    2 空间热控技术北京市重点实验室，北京100094
  • 出版日期:2021-04-25 发布日期:2021-04-07

Analysis of the influence of Mars surface thermal environment on spacecraft thermal control

ZHANG Bingqiang，XIANG Yanchao，XUE Shuyan，ZHENG Kai，ZHONG Qi，ZHANG Youwei   

  1. 1 Beijing Institute of Spacecraft System Engineering，Beijing 100094，China
    2 Beijing Key Laboratory of Space Thermal Control Technology，Beijing 100094，China
  • Published:2021-04-25 Online:2021-04-07

PDF (PC)

334

摘要： 火星大气对太阳辐射产生吸收和散射作用，同时还将与火星表面航天器发生对流换热。热设计时难以直接评估对流、辐射和导热三种换热对航天器的影响，从而确定主要的控温途径。在调研火星表面辐射、大气等热环境的基础上，从线性化传热系数和对流辐射比的角度对比分析了辐射、对流和导热对航天器的影响。器表辐射传热系数随光学属性和温度的变化范围为0.3～1.4W/(m2·℃)，对流传热系数随风速变化为0.2～1.5W/(m2·℃)，器内导热传热系数可控制在0.25W/(m2·℃)以下。结果表明，太阳辐射较火星表面和天空辐射而言是主要外热源，航天器表面的辐射和对流换热为两条并联换热途径，两者均可成为主要换热途径，器内导热传热是控制航天器内外隔热的主要可控因素。

关键词: 火星, 热环境, 对流换热, 辐射换热, 导热换热, 航天器热控

Abstract: For the Mars surface exploration, the Martian atmosphere absorbs and scatters the incident solar radiation, while causing convective heat transfer between itself and the spacecraft on the surface of Mars. In the thermal design, it is difficult to directly assess the impact of the three heat transfer types (convection, radiation and heat conduction) on the spacecraft and determine the main transmission ways. Based on the investigation into the thermal environment such as Mars surface radiation and the atmosphere, the effects of radiation, convection and heat conduction on the spacecraft were compared and analyzed from the perspective of linearized heat transfer coefficient and convection-radiation ratio. The radiation heat transfer coefficient of the spacecraft surface varies with optical properties and temperature in the range of 0.3W/(m2·℃) to 1.4W/(m2·℃), and the convective heat transfer coefficient varies with the wind speed from 0.2W/(m2·℃) to 1.5W/(m2·℃). The conduction heat transfer coefficient can be controlled below 0.25W/(m2·℃). The results show that solar radiation is the main external heat source compared to Mars surface and sky radiation. Radiation and convective heat transfer on the surface of the spacecraft are two parallel transmission paths, both of which may become the main path. The heat conduction in the spacecraft is the main controllable factor of its thermal control.

Key words: Mars, thermal environment, convection heat transfer, radiation heat transfer, conductivity heat transfer, spacecraft thermal control